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GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il)
Reynolds number: 100,000
Max Cl/Cd: 56.33 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe140-il-100000-n5.txt
Download as CSV file: xf-goe140-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 140 (MVA H.17) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2818   0.09572   0.09131  -0.0250   1.0000   0.0462
  -7.250  -0.2825   0.09417   0.08986  -0.0288   1.0000   0.0468
  -7.000  -0.2804   0.09217   0.08793  -0.0326   1.0000   0.0471
  -6.750  -0.2774   0.08990   0.08571  -0.0354   1.0000   0.0472
  -6.250  -0.2481   0.08035   0.07622  -0.0365   0.9895   0.0486
  -5.750  -0.1775   0.07192   0.06759  -0.0536   0.9666   0.0572
  -5.500  -0.1264   0.06752   0.06285  -0.0679   0.9523   0.0580
  -5.250  -0.1119   0.06245   0.05790  -0.0671   0.9405   0.0589
  -5.000  -0.0886   0.05889   0.05432  -0.0686   0.9270   0.0610
  -4.750  -0.0363   0.05605   0.05103  -0.0793   0.9113   0.0684
  -4.500  -0.0014   0.05216   0.04686  -0.0840   0.8962   0.0690
  -4.250   0.0197   0.04808   0.04281  -0.0848   0.8804   0.0700
  -4.000   0.0458   0.04509   0.03972  -0.0863   0.8636   0.0717
  -3.750   0.0752   0.04256   0.03699  -0.0883   0.8463   0.0753
  -3.500   0.1147   0.04034   0.03422  -0.0920   0.8292   0.0815
  -3.250   0.1396   0.03761   0.03138  -0.0927   0.8110   0.0828
  -2.750   0.2073   0.03191   0.02473  -0.0950   0.7757   0.0571
  -2.500   0.2350   0.02992   0.02251  -0.0955   0.7572   0.0558
  -2.250   0.2646   0.02820   0.02045  -0.0960   0.7385   0.0552
  -2.000   0.2955   0.02687   0.01865  -0.0962   0.7192   0.0570
  -1.750   0.3244   0.02548   0.01695  -0.0964   0.6998   0.0568
  -1.500   0.3530   0.02421   0.01535  -0.0964   0.6805   0.0560
  -1.000   0.4104   0.02213   0.01262  -0.0963   0.6430   0.0551
  -0.750   0.4389   0.02128   0.01145  -0.0961   0.6244   0.0550
  -0.500   0.4670   0.02055   0.01042  -0.0959   0.6064   0.0553
  -0.250   0.4949   0.01991   0.00952  -0.0956   0.5893   0.0559
   0.000   0.5226   0.01936   0.00872  -0.0952   0.5725   0.0568
   0.250   0.5498   0.01896   0.00817  -0.0950   0.5563   0.0592
   0.500   0.5767   0.01874   0.00788  -0.0948   0.5409   0.0635
   0.750   0.6038   0.01843   0.00743  -0.0945   0.5262   0.0661
   1.000   0.6304   0.01815   0.00703  -0.0941   0.5123   0.0680
   1.250   0.6568   0.01787   0.00671  -0.0937   0.4992   0.0708
   1.500   0.6836   0.01774   0.00649  -0.0934   0.4871   0.0757
   1.750   0.7110   0.01767   0.00625  -0.0933   0.4758   0.0836
   2.000   0.7385   0.01764   0.00611  -0.0932   0.4653   0.0997
   2.250   0.7661   0.01761   0.00616  -0.0933   0.4550   0.1442
   2.500   0.7873   0.01602   0.00618  -0.0919   0.4469   1.0000
   2.750   0.8143   0.01631   0.00629  -0.0917   0.4377   1.0000
   3.000   0.8411   0.01663   0.00644  -0.0915   0.4293   1.0000
   3.250   0.8678   0.01694   0.00664  -0.0913   0.4212   1.0000
   3.500   0.8945   0.01727   0.00688  -0.0912   0.4135   1.0000
   3.750   0.9211   0.01761   0.00713  -0.0910   0.4064   1.0000
   4.000   0.9477   0.01797   0.00744  -0.0909   0.4000   1.0000
   4.250   0.9742   0.01832   0.00778  -0.0907   0.3936   1.0000
   4.750   1.0270   0.01909   0.00853  -0.0904   0.3825   1.0000
   5.000   1.0533   0.01949   0.00893  -0.0903   0.3773   1.0000
   5.250   1.0794   0.01991   0.00931  -0.0901   0.3730   1.0000
   5.500   1.1054   0.02032   0.00984  -0.0899   0.3670   1.0000
   5.750   1.1311   0.02072   0.01027  -0.0897   0.3615   1.0000
   6.000   1.1567   0.02114   0.01072  -0.0894   0.3565   1.0000
   6.250   1.1814   0.02149   0.01117  -0.0891   0.3483   1.0000
   6.500   1.2049   0.02175   0.01150  -0.0885   0.3370   1.0000
   6.750   1.2280   0.02202   0.01180  -0.0879   0.3257   1.0000
   7.000   1.2513   0.02234   0.01219  -0.0873   0.3155   1.0000
   7.250   1.2734   0.02263   0.01254  -0.0866   0.3010   1.0000
   7.500   1.2945   0.02298   0.01293  -0.0857   0.2843   1.0000
   7.750   1.3169   0.02339   0.01347  -0.0851   0.2714   1.0000
   8.000   1.3378   0.02387   0.01399  -0.0842   0.2546   1.0000
   8.250   1.3584   0.02443   0.01461  -0.0834   0.2332   1.0000
   8.500   1.3762   0.02523   0.01533  -0.0822   0.1987   1.0000
   8.750   1.3787   0.02748   0.01695  -0.0797   0.1152   1.0000
   9.000   1.3874   0.02924   0.01863  -0.0776   0.0886   1.0000
   9.250   1.3796   0.03232   0.02132  -0.0741   0.0276   1.0000
   9.500   1.3806   0.03424   0.02330  -0.0713   0.0239   1.0000
   9.750   1.3815   0.03598   0.02517  -0.0685   0.0223   1.0000
  10.000   1.3826   0.03787   0.02726  -0.0662   0.0216   1.0000
  10.250   1.3816   0.04010   0.02970  -0.0643   0.0210   1.0000
  10.500   1.3787   0.04276   0.03257  -0.0629   0.0206   1.0000
  10.750   1.3736   0.04591   0.03594  -0.0621   0.0202   1.0000
  11.000   1.3663   0.04965   0.03990  -0.0620   0.0200   1.0000
  11.250   1.3568   0.05401   0.04447  -0.0625   0.0197   1.0000
  11.500   1.3451   0.05900   0.04971  -0.0635   0.0195   1.0000
  11.750   1.3320   0.06447   0.05539  -0.0650   0.0194   1.0000
  12.000   1.3176   0.07031   0.06142  -0.0667   0.0193   1.0000
  12.250   1.3031   0.07625   0.06754  -0.0684   0.0191   1.0000
  12.500   1.2892   0.08214   0.07359  -0.0701   0.0190   1.0000
  12.750   1.2759   0.08792   0.07953  -0.0717   0.0188   1.0000
  13.000   1.2640   0.09351   0.08527  -0.0732   0.0187   1.0000
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